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74-130 WP2 MOD (fx74130wp2mod-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: 74-130 WP2 MOD (fx74130wp2mod-il)
Reynolds number: 500,000
Max Cl/Cd: 110.51 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx74130wp2mod-il-500000-n5.txt
Download as CSV file: xf-fx74130wp2mod-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: 74-130 WP2 MOD                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.1688   0.08757   0.08422  -0.0964   0.7965   0.0098
  -9.750  -0.1659   0.08407   0.08073  -0.0982   0.7954   0.0104
  -9.500  -0.1655   0.08012   0.07680  -0.1000   0.7943   0.0092
  -9.250  -0.1633   0.07674   0.07343  -0.1018   0.7932   0.0099
  -9.000  -0.1600   0.07214   0.06884  -0.1057   0.7917   0.0119
  -8.750  -0.1612   0.06784   0.06458  -0.1087   0.7902   0.0119
  -8.500  -0.1665   0.06306   0.05982  -0.1128   0.7885   0.0120
  -8.000  -0.1968   0.05625   0.05300  -0.1127   0.7840   0.0099
  -6.750  -0.1887   0.03439   0.03017  -0.1091   0.7716   0.0076
  -6.500  -0.1797   0.03094   0.02644  -0.1079   0.7697   0.0074
  -6.250  -0.1665   0.02764   0.02284  -0.1066   0.7681   0.0072
  -6.000  -0.1503   0.02457   0.01939  -0.1053   0.7667   0.0070
  -5.750  -0.1318   0.02155   0.01596  -0.1040   0.7653   0.0069
  -5.500  -0.1101   0.01929   0.01334  -0.1032   0.7640   0.0067
  -5.250  -0.0868   0.01738   0.01113  -0.1025   0.7624   0.0068
  -5.000  -0.0622   0.01595   0.00945  -0.1019   0.7606   0.0069
  -4.750  -0.0370   0.01486   0.00819  -0.1015   0.7588   0.0071
  -4.500  -0.0116   0.01402   0.00723  -0.1012   0.7570   0.0074
  -4.250   0.0143   0.01340   0.00648  -0.1010   0.7554   0.0077
  -4.000   0.0391   0.01262   0.00561  -0.1007   0.7538   0.0081
  -3.750   0.0645   0.01203   0.00496  -0.1005   0.7522   0.0087
  -3.500   0.0910   0.01167   0.00456  -0.1005   0.7507   0.0094
  -3.250   0.1174   0.01139   0.00428  -0.1005   0.7486   0.0104
  -3.000   0.1439   0.01109   0.00394  -0.1004   0.7462   0.0112
  -2.750   0.1706   0.01077   0.00357  -0.1004   0.7439   0.0117
  -2.500   0.1977   0.01049   0.00323  -0.1005   0.7418   0.0126
  -2.250   0.2250   0.01023   0.00294  -0.1005   0.7398   0.0168
  -2.000   0.2524   0.00997   0.00273  -0.1007   0.7380   0.0386
  -1.750   0.2788   0.00956   0.00256  -0.1009   0.7359   0.1184
  -1.500   0.3001   0.00798   0.00237  -0.1012   0.7330   0.5275
  -1.250   0.3223   0.00746   0.00262  -0.1001   0.7301   0.7519
  -1.000   0.3497   0.00759   0.00272  -0.0999   0.7272   0.7914
  -0.750   0.3759   0.00773   0.00284  -0.0994   0.7247   0.8117
  -0.500   0.4029   0.00782   0.00290  -0.0992   0.7220   0.8229
  -0.250   0.4300   0.00788   0.00295  -0.0991   0.7184   0.8304
   0.000   0.4574   0.00789   0.00294  -0.0991   0.7148   0.8354
   0.250   0.4850   0.00789   0.00291  -0.0991   0.7117   0.8387
   0.500   0.5132   0.00789   0.00288  -0.0994   0.7084   0.8413
   0.750   0.5414   0.00790   0.00288  -0.0997   0.7039   0.8434
   1.000   0.5699   0.00790   0.00285  -0.1001   0.6996   0.8453
   1.250   0.5986   0.00789   0.00281  -0.1005   0.6955   0.8469
   1.500   0.6264   0.00789   0.00282  -0.1007   0.6899   0.8479
   1.750   0.6542   0.00788   0.00281  -0.1009   0.6847   0.8490
   2.000   0.6820   0.00789   0.00282  -0.1012   0.6794   0.8501
   2.250   0.7098   0.00790   0.00283  -0.1014   0.6734   0.8510
   2.500   0.7376   0.00793   0.00284  -0.1016   0.6679   0.8521
   2.750   0.7651   0.00796   0.00290  -0.1018   0.6614   0.8533
   3.000   0.7926   0.00801   0.00293  -0.1020   0.6555   0.8544
   3.250   0.8201   0.00806   0.00300  -0.1022   0.6486   0.8554
   3.750   0.8746   0.00821   0.00317  -0.1026   0.6358   0.8574
   4.000   0.9012   0.00831   0.00326  -0.1026   0.6284   0.8586
   4.250   0.9270   0.00844   0.00337  -0.1025   0.6162   0.8598
   4.500   0.9514   0.00863   0.00350  -0.1021   0.5996   0.8609
   4.750   0.9747   0.00882   0.00366  -0.1014   0.5808   0.8618
   5.000   0.9970   0.00906   0.00386  -0.1006   0.5613   0.8629
   5.250   1.0196   0.00930   0.00407  -0.0999   0.5440   0.8639
   5.500   1.0394   0.00962   0.00432  -0.0987   0.5164   0.8652
   5.750   1.0555   0.01007   0.00463  -0.0968   0.4738   0.8667
   6.000   1.0633   0.01084   0.00512  -0.0935   0.4068   0.8689
   6.250   1.0624   0.01194   0.00588  -0.0888   0.3374   0.8715
   6.500   1.0628   0.01281   0.00653  -0.0842   0.2879   0.8739
   6.750   1.0618   0.01381   0.00731  -0.0797   0.2386   0.8763
   7.000   1.0614   0.01489   0.00818  -0.0756   0.1918   0.8790
   7.250   1.0642   0.01596   0.00909  -0.0722   0.1528   0.8819
   7.500   1.0693   0.01702   0.01001  -0.0694   0.1197   0.8848
   7.750   1.0761   0.01808   0.01095  -0.0670   0.0921   0.8878
   8.000   1.0831   0.01914   0.01192  -0.0646   0.0676   0.8911
   8.250   1.0912   0.02017   0.01290  -0.0625   0.0486   0.8950
   8.500   1.1011   0.02115   0.01384  -0.0606   0.0359   0.8990
   9.000   1.1229   0.02298   0.01569  -0.0572   0.0211   0.9086
   9.250   1.1343   0.02387   0.01662  -0.0557   0.0171   0.9157
   9.500   1.1459   0.02473   0.01754  -0.0540   0.0143   0.9262
  10.000   1.1723   0.02669   0.01963  -0.0521   0.0088   1.0000
  10.250   1.1837   0.02784   0.02081  -0.0509   0.0069   1.0000
  10.500   1.1943   0.02908   0.02212  -0.0497   0.0059   1.0000
  10.750   1.2058   0.03027   0.02339  -0.0486   0.0054   1.0000
  11.000   1.2165   0.03153   0.02473  -0.0474   0.0050   1.0000
  11.250   1.2266   0.03286   0.02614  -0.0463   0.0046   1.0000
  11.500   1.2352   0.03435   0.02770  -0.0451   0.0042   1.0000
  11.750   1.2424   0.03600   0.02943  -0.0438   0.0039   1.0000
  12.000   1.2485   0.03780   0.03132  -0.0426   0.0037   1.0000
  12.250   1.2535   0.03976   0.03339  -0.0413   0.0036   1.0000
  12.500   1.2613   0.04149   0.03522  -0.0404   0.0035   1.0000
  12.750   1.2693   0.04324   0.03708  -0.0395   0.0035   1.0000
  13.000   1.2771   0.04506   0.03903  -0.0387   0.0033   1.0000
  13.250   1.2830   0.04712   0.04121  -0.0379   0.0032   1.0000
  13.500   1.2906   0.04906   0.04325  -0.0373   0.0030   1.0000
  13.750   1.2957   0.05129   0.04560  -0.0367   0.0029   1.0000
  14.000   1.3010   0.05357   0.04799  -0.0362   0.0028   1.0000
  14.250   1.3055   0.05600   0.05055  -0.0357   0.0028   1.0000
  14.500   1.3088   0.05863   0.05332  -0.0353   0.0027   1.0000
  14.750   1.3114   0.06140   0.05623  -0.0350   0.0027   1.0000
  15.000   1.3136   0.06430   0.05926  -0.0349   0.0026   1.0000
  15.250   1.3149   0.06740   0.06250  -0.0349   0.0026   1.0000
  15.500   1.3152   0.07070   0.06594  -0.0351   0.0025   1.0000
  15.750   1.3142   0.07424   0.06964  -0.0354   0.0025   1.0000
  16.000   1.3121   0.07805   0.07361  -0.0359   0.0024   1.0000
  16.250   1.3093   0.08206   0.07776  -0.0367   0.0024   1.0000
  16.500   1.3050   0.08640   0.08227  -0.0377   0.0023   1.0000
  16.750   1.2987   0.09118   0.08724  -0.0389   0.0023   1.0000
  17.000   1.2923   0.09610   0.09231  -0.0405   0.0023   1.0000
  17.250   1.2836   0.10156   0.09795  -0.0424   0.0023   1.0000
  17.500   1.2739   0.10741   0.10397  -0.0448   0.0022   1.0000
  17.750   1.2630   0.11367   0.11041  -0.0475   0.0022   1.0000
  18.000   1.2509   0.12039   0.11730  -0.0508   0.0022   1.0000
  18.250   1.2378   0.12760   0.12469  -0.0545   0.0022   1.0000
  18.500   1.2249   0.13509   0.13234  -0.0588   0.0022   1.0000
  18.750   1.2097   0.14339   0.14082  -0.0636   0.0022   1.0000
  19.000   1.1943   0.15215   0.14975  -0.0690   0.0022   1.0000
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